42results about "Airbags" patented technology

The invention discloses an electric aircraft, a power distribution system, a power supply control method and a computer storage medium, and the power distribution system of the electric aircraft comprises a first battery pack, a second battery pack, a first isolation device and a second isolation device. Wherein the first battery pack and the second battery pack supply power to the first part of rotor wing motors through the first isolation device, supply power to the second part of rotor wing motors through the second isolation device, and the first isolation device and the second isolation device perform isolation and power reconstruction of a fault line when the power distribution system has a power supply fault. The embodiment of the invention is simple in structure and low in cost.

The present disclosure discloses a landing aid for a parachutist, in particular for a tandem jump or landing with heavy equipment, having an air bag, which protects the parachutist during landing, wherein the air bag has an inflow opening through which air can flow into the air bag in order to fill it by means of the airstream. It is provided that the landing aid comprises a spring element, by means of which the inflow opening is held in the correct position with respect to the air flow and / or an unpacking process of the air bag is supported.

Managing a package delivery system deploying an unmanned vehicle including an inflatable unit for reducing package vibration in a transportation vehicle. Package data is received at a computer, and the package data includes package descriptions. Spatial positioning of the packages in the transport space is tracked to determine, spatial positioning changes between the packages in the transport space based on the package data received at the computer and the transport. One or more unmanned vehicles are delivered to the transport space based on the spatial positioning changes in the transport space, and the unmanned vehicles including inflatable units. The inflatable units are deployed in the transport space by inflating the inflatable units at locations in the transport space based on the spatial positioning changes to discourage package movement in the transport space.

Disclosed in the present application are an electric aircraft, a power distribution system, a power supply control method and a computer storage medium. The power distribution system of the electric aircraft comprises: a first battery pack, a second battery pack, a first isolation device and a second isolation device; the first battery pack and the second battery pack supply power to first rotor motors by means of the first isolation device, and supply power to second rotor motors by means of the second isolation device; when a power supply fault occurs in the power distribution system, the first isolation device and the second isolation device isolate a faulty line and perform power reconfiguration. The embodiments of the present application have simple structures and low costs.

A retractable cargo hook for aircraft is described. The cargo hook including a torsion spring allowing rotatable attachment to an aircraft body. An optional recessed portion of the aircraft body can house and receive the cargo hook. This can protect interior components from crashes which can push the cargo hook into the aircraft fuselage, damaging components.

An unmanned cargo loading and transport system adapted for operation with an unmanned aerial vehicle (UAV) comprising a payload pad comprising a plurality of support members movable from an extended mode to a retracted mode when exposed to a lateral force applied to the support members and a payload container adapted to attach to a UAV and pick up cargo from the payload pad by transferring the weight of the cargo from the payload pad to the payload container. The lower portion of the payload container comprises two generally opposed cargo doors movably mounted at opposed sides and movable inwardly to a closed position and outwardly to an open position to receive cargo when the payload container is positioned at the payload pad. The system further comprises a motive power mechanism coupled to the cargo doors for selectively moving the doors between their open and their closed positions.

Cargo packaging system for a mobility vehicle, the system comprising: a housing (20) having an interior space therein for receiving cargo and mounted on the mobility vehicle; a plurality of air cushions (10) provided at a plurality of positions on an inner surface of the housing (20) and exerting pressure on the cargo accommodated in the housing (20) and cushioning it during its expansion in a plurality of directions; an air charging part (30) connected to the plurality of air cushions and configured to inject gas into each air cushion of the housing (20) and to control a flow rate or pressure of the injected gas; an outlet controlled by the air charging part (30) and discharging the gas injected into each air cushion (10) to the outside of the outlet; and further comprising a heat exchanger (40) for heating or cooling the gas injected into each air cushion (10) by heat exchange, wherein the heat exchanger (40) is mounted downstream of the air charging part (30).

The invention discloses a household intelligent, light, safe and folding type small manned aircraft which comprises a ground walking system, a rotor wing flight system, a cabin, a fixed wing flight system and the like, and the ground walking system comprises tire supporting legs, stress spring sensors and driving motors; the rotor wing flight system comprises a foldable machine arm, a motor, a rotor wing and an anti-collision radar; the fixed wing flight system comprises a foldable fixed wing, a motor and a rotor wing. The aircraft top adopts the inflatable low-cost parachute, the aircraft bottom adopts the anti-falling safety airbag, the wings are provided with the anti-collision radars, and the micro laser ranging radar is arranged in front, so that the aircraft is safe and reliable to use. The structural part is made of the carbon fiber material, so that the weight is light. The foldable electric vehicle has the advantages of being reasonable in structure, high in practicability, small in size, light in weight, foldable, high in controllability, low in cost, safe, reliable and high in intelligent degree.

The present application relates to an aerial maneuvering apparatus, a control method thereof, and a computer-readable storage medium. An aerial maneuvering apparatus includes a seat in which a safety airbag and a parachute are stored, and an escape portion configured to support the seat mounted to the escape portion, coupled to the aerial maneuvering apparatus to form a part of the aerial maneuvering apparatus, and configured to enable a passenger to perform an emergency jump with the seat to the outside of the aerial maneuvering apparatus when the escape portion is separated from the aerial maneuvering apparatus.

A fuel supply apparatus includes a plurality of supply systems; a supply control device provided in each of the supply systems; a supply pipe communicating each of the supply systems and each of rear facilities; a supply member interposed in the supply pipe and connected to each of the supply control devices; and a supply hose connected to the supply pipe, the supply hose having a supply nozzle at its tip, wherein the supply control device includes: a function of determining whether or not communication filling is established in one side of the supply system / or the other side of the supply system; and when communication filling is not established in the supply system on the one side and communication filling is established in the supply system on the other side, a function of supplying using vehicle side data in the supply system on the other side.

A high-pressure gas tank is provided with: a tank main body provided with a main body part and a dome part disposed on one side of the main body part in the axial direction; a joint having a shaft portion extending in the axial direction from the center of the dome portion, and a through hole penetrating the shaft portion so as to allow gas to flow therethrough; and a protective member having a resin protective portion covering the dome portion around the joint, and a ring-shaped or cylindrical metal connecting portion integrated with the protective portion and into which the shaft portion of the joint is inserted. The joint is provided with a first threaded portion on the outer periphery of the shaft portion, and the protective member is provided with a second threaded portion on the inner periphery of the connecting portion, the second threaded portion being screwed to the first threaded portion.

The invention discloses a household intelligent, lightweight, safe, folding small manned aircraft, which comprises a ground driving system, a rotor wing flight system, a cabin (10) and a fixed wing flight system (13, 14). The ground driving system comprises a tire leg (5), a force spring sensor (6) and a driving motor; The rotor wing flight system includes a folding arm (2), a motor (3), a rotor wing (4) and an anti-collision radar. The fixed-wing flight system consists of foldable fixed wings (13, 14), motors and a rotor wing (12). The top of the aircraft adopts an inflatable low cost parachute (9), the bottom adopts an anti-fall airbag, the wing is provided with an anti-collision radar, and the front is provided with a micro laser ranging radar, which is safe and reliable to use. The structure of the invention adopts optionally carbon fiber material, which makes the weight light.

Provided is a drone with an airbag with which it is possible to prevent the danger of injuring a person when a crashed drone collides with the person. A first airbag 11 is provided in a state surrounding a drone 9 within the horizontal plane. The first airbag 11 is held by a first holding part 10 provided on a central mounting part 2. The first airbag 11 is installed in the first holding part 10 in a folded state, the first airbag 11 being inflatable so as to project outward by gas being supplied. The first airbag 11 is capable of expanding before impacting another object such as a person and surrounding the drone 9 in the horizontal plane.

Provided is a reusable airbag inflator including a gas cartridge mounted with an opening or closing valve capable of being opened or closed to discharge a compression gas stored therein, a driving portion for opening or closing the opening or closing valve, and an opening or closing body including a first coupling hole where the opening or closing valve is installed, a second coupling hole where the driving portion is installed, a discharge hole through which the compression gas is discharged to an airbag, and a body cavity connecting the first coupling hole, the second coupling hole, and the discharge hole, wherein the opening or closing valve is a check valve that is opened when external force greater than internal pressure of the gas cartridge is received and closed when the external force is removed.

The present invention discloses a rapid gas cylinder release device and a release method. The device includes a gas cylinder and a gas nozzle, and is characterized in that: the gas nozzle has a first channel connecting the gas cylinder and a second channel connecting an airbag. When the rotary valve core is in the first position, the channels are disconnected, and when it rotates to the second position, the channels are connected; a puncturing needle for puncturing the sealing film of the gas cylinder when connecting the gas cylinder is provided in the first channel; a rocker arm is fixed on the valve rod, and a torsion spring and an electromagnet are provided. When the iron core of the electromagnet is in the extended state, it limits the rocker arm to keep the rotary valve core in the first position and the rocker arm compresses the torsion spring to make the torsion spring in a pre-tightened state. When the iron core of the electromagnet is in the retracted state, it releases the rocker arm, and under the action of the torsion spring, the rocker arm drives the valve rod to rotate the rotary valve core to the second position. The present invention first punctures the gas cylinder to form a high-pressure sealed area. When the gas needs to be released, the valve core is quickly driven to open the gas channel through the release of the torsion spring. It can effectively improve the gas release speed and meet the requirements of human fall protection.

An aircraft (600) comprises ducted fans (609). The ducted fans (609) are an array of ducted fans (603). An array of ducted fans (603) is integrated in a wing (605) of the aircraft. A ducted fan (609) may be integrated in a horizontal tail (611) of the aircraft. The wing (605) includes a movable edge (603A), such as a flap, to provide both exhaust area and flow turning control. The movable edge (603A) is articulated by pivoting the movable edge. The movable edge (603A) may be extended and retracted.

The present invention discloses an attached drone anti-water bionic airbag device, comprising a main body, an airbag device, a power switch, a distance detector, an acceleration detector, a GPS locator, a PE hexagonal roller, an elastic nylon rope, and an adhesive sheet. The power switch, distance detector, acceleration detector, and GPS locator are fixed to the main body. The PE hexagonal rollers are arranged in parallel to form a plurality of PE hexagonal roller belts. One end of the elastic nylon rope is connected to the main body, and one end of the elastic nylon rope passes through the PE hexagonal roller belt and is connected to the adhesive sheet. The adhesive sheet and the PE hexagonal roller belt are respectively provided with two and connected to both sides of the main body. The present invention combines the low density, light weight, and corrosion resistance of PE material to design the device main body. It is equipped with an infrared distance sensor, a drone acceleration monitoring sensor, a GPS satellite positioning system, a trigger-type airbag, and an audible and visual alarm system, providing multi-faceted safety protection for drones that fail and fall into the water.

An aircraft may comprise ducted fans. The ducted fans may be an array of ducted fans. An array of ducted fans may be integrated in a wing of the aircraft. A ducted fan may be integrated in a horizontal tail of the aircraft. The wing may include a movable edge, such as a flap, to provide both exhaust area and flow turning control. The movable edge may be articulated by pivoting the movable edge. The movable edge may be extended and retracted.

An aircraft may include a ducted fan. The ducted fan may be an array of ducted fans. An array of ducted fans may be integrated in a wing of an aircraft. The ducted fan may be integrated in a horizontal tail of an aircraft. The wing may include a movable edge, such as a flap, to provide both an exhaust area and flow steering control. The movable edge may be hinged by pivoting the movable edge. The movable edge may extend and retract.

A vertical take-off and landing aircraft of the tail-sitting type comprises a cockpit integrated into a body having delta wings in the rear section with respect to the cockpit and a propulsion system placed in the front section with respect to the cockpit. The propulsion system includes at least two coaxial counter-rotating propellers put into rotation by at least two electric engines powered by rechargeable batteries.

The invention provides a cold air type gas generator and a using method thereof, and belongs to the technical field of gas generators, the cold air type gas generator comprises a gas cylinder and a trigger device, the trigger device is fixed at a gas outlet of the gas cylinder, the trigger device comprises a shell, a valve needle is slidably connected in the shell, a first vent hole is formed in one end of the shell, and a second vent hole is formed in the other end of the shell; a spring is fixedly connected between the valve needle and the ignition seat, and the end part of the valve needle is arranged close to the first vent hole. The gas cylinder can be inflated again after the cold air type gas generator releases gas, the gas cylinder does not need to be replaced, repeated use of the gas cylinder is achieved, and the single-time use cost of the cold air type gas generator is reduced.

A high-pressure gas tank includes: a tank body including a body portion and a dome portion disposed on one side of the body portion in the axial direction; a cap having a shaft portion extending from a central portion of the dome portion along the axial direction and a through-hole through which the gas flows through the shaft portion; and a protective member that includes a protective portion covering the dome portion around the cap and made of resin and a connecting portion integrated with the protective portion, having an annular shape or a tubular shape into which the shaft portion of the cap is inserted, and made of metal. The cap includes a first threaded portion on an outer periphery of the shaft portion, and the protective member includes a second threaded portion screwed to the first threaded portion on an inner periphery of the connecting portion.

The invention relates to the technical field of aircrafts, in particular to an aircraft fuselage safety air bag protection device which comprises a fuselage and a seat body and further comprises box bodies bolted to the two sides of the interior of the fuselage, first air bags are fixed to the interiors of the box bodies, and an air pump is bolted to the upper portion of the interior of the seat body; the outlet end of the air pump communicates with an air conveying pipe, a connecting box is further bolted in the seat body, and the end, away from the air pump, of the air conveying pipe communicates with the connecting box; by starting an air pump, external air enters a storage box through an air conveying pipe, a connecting box and a vertical pipe, high-pressure air exists in the storage box, meanwhile, in the process of supplying air into the storage box, an impeller is pushed to rotate to drive a transmission rod and a transverse rod to rotate, a transmission column is driven to rotate, and therefore a rotating disc and a massage block rotate; the back of the driver is massaged, and the fatigue of the driver is relieved.

This invention relates to the field of aircraft technology, and more particularly to an aircraft fuselage airbag protection device, comprising an airframe and a seat body, and further comprising: a box attached to both sides inside the airframe, wherein a first airbag is fixed inside the box; an air pump is attached to the upper part inside the seat body, and an air supply pipe is connected to the outlet end of the air pump; a connecting box is also attached to the inside of the seat body, and the end of the air supply pipe away from the air pump is connected to the connecting box; the invention allows external gas to enter the storage tank through the air supply pipe, connecting box, and vertical pipe when the air pump is turned on, creating high-pressure gas inside the storage tank; simultaneously, during the air supply process, the impeller is rotated, which drives the transmission rod and crossbar to rotate, and drives the transmission column to rotate, thereby rotating the turntable and massage block to massage the pilot's back and relieve pilot fatigue.

An electronic module assembly (EMA) for use in controlling one or more personal restraint systems. A programmed processor within the EMA is configured to determine when a personal restraint system associated with each seat in a vehicle should be deployed. In addition, the programmed processor is configured to perform a diagnostic self-test to determine if the EMA and the personal restraint systems are operational. In one embodiment, results of the diagnostic self-test routine are displayed on a display included on the electronic module assembly. In an alternative embodiment, the results of the diagnostic self-test routine are transmitted via a wireless transceiver to a remote device. The remote device can include a wireless interrogator or can be a remote computer system such as a cabin management computer system.

To provide a technique for suppressing a load on a tank when fixing a protection member to the tank.SOLUTION: A high pressure gas tank 10 includes a tank body 10a including a trunk part 12, and dome parts 14, 16 arranged on one side in the axial direction of the trunk part 12, a mouth piece 30 having a shaft part 32 extending from the center of the dome part 14 along the axial direction and a through-hole 36 passing through the shaft part 32 so that gas can be distributed thereinto, and a protection member 50 having a resin protection part 52 covering the dome part 14 around the mouth piece 30 and an annular or cylindrical metal connection part 54 which is integrated with the protection part 52 and into which the shaft part 32 of the mouth piece 30 is inserted, the mouth piece 30 including a first screw part 38 provided on the outer periphery of the shaft part 32, the protection member 50 including a second screw part 58 provided on the inner periphery of the connection part 54 and threaded to the first screw part 38.SELECTED DRAWING: Figure 2

An aircraft may comprise ducted fans. The ducted fans may be an array of ducted fans. An array of ducted fans may be integrated in a wing of the aircraft. A ducted fan may be integrated in a horizontal tail of the aircraft. The wing may include a movable edge, such as a flap, to provide both exhaust area and flow turning control. The movable edge may be articulated by pivoting the movable edge. The movable edge may be extended and retracted.

An aircraft may comprise ducted fans. The ducted fans may be an array of ducted fans. An array of ducted fans may be integrated in a wing of the aircraft. A ducted fan may be integrated in a horizontal tail of the aircraft. The wing may include a movable edge, such as a flap, to provide both exhaust area and flow turning control. The movable edge may be articulated by pivoting the movable edge. The movable edge may be extended and retracted.

The disclosure relates to a transitional aircraft. Specifically, the disclosure relates to a transitional aerial vehicle (AV), having a closed polygonal wing member allowing for, inter-alia; smaller dimensions (footprint) compared to AV with same lift / wing surface, higher payload capacity, vertical take-off and landing (VTOL), versatile flight modes (e.g., VTOL, hover, fixed wing cruising, side-to-side flight), effective work with rotors mounted with fixed longitudinal and transverse angle deflection in two arrays, longer flight time and distance, and the ability to self-stabilize landing on and taking off from uneven surfaces, with methods and modular systems for selectably releasing and protecting incorporated payload controllably inflated air-bags.

The present invention relates to a body (2) which is the aircraft, at least one airbag assembly (3) that is located on the body (2) and protects the pilot and / or the passenger, at least one sensor (4) that detects the active or inactive status of the airbag assembly (3), and at least one activation apparatus (5) that is located on the body (2) and enables the airbag assembly (3) to operate when triggered by the user.